PDF Publication Title:
Text from PDF Page: 004
3 FIG. 5 is a plan view of two ?rst-stage nozzle parti tions according to the invention with associated absolute gas velocity vectors; FIGS. 6 and 7 are plan views and elevation views re spectively of a typical “free vortex bucket” in accordance withthepriorart; FIGS. 8 and 9 are plan and elevation views of a tur bine bucket according to the invention, having the same root cross-sections as in FIGS. 6 and 7, for comparison; FIG. 10 is a graph of actual and allowable stress vs. 10 temperature; FIG. 11 is a graph of bucket dimension vs. allowable local bucket temperature; and FIG. 12 is a graph of normalized net cross-sectional area of a bucket vs. bucket dimension. Brie?y stated, the invention is practiced by providing means to “slant” the temperature pro?le of the hot gas entering the ?rst-stage nozzle so that the gas tempera ture increases with the radius, being much higher toward the outer part of the flow annulus than has previously beenthoughtpracticable. Thenozzleandbucketblade angles are then designed, with the aid of the velocity di agram, so as to cause the tangential Mach number of the gas to vary inversely with the radius, a procedure which gives radial equilibrium of the gas while compensating for 25 itsgradientintemperature. Thebucketisthendesigned to have a “gross” (exposed to the gas) cross-section which increases with radius to provide aerodynamic stability, while at the same time its “net” (actual metal) cross section is caused to vary as a more complicated function 30 oftheradius. Thisisdoneinsuchamannerastocause the actual stress distribution from root to tip to substan tially conform with the allowable stress of the selected bucket material for the selected radial temperature gradient. 4 angles may be varied from those of the reference radius in order to achieve a desired aerodynamic relationship at differentradii. Forexample,inthe“freevortex"design which assumes constant gas temperature over the blade height, the nozzle and blade angles are caused to con form to a ?ow pattern, wherein the whirl velocity or tangential velocity component of the gas varies inversely with the radius and where the axial velocity component is constant over the blade height, as in Equation 1. The vector diagram for a prior art free vortex design may be seen by reference to FIG. 3, wherein the vectors OWR andOWT representthetangentialvelocitiesofthe bucketrootandbuckettiprespectively. ThevectorOR; is the absolute gas velocity leaving the nozzle at the root. Thus, the difference between vector OR; and the bucket rootvelocityOWR istheenteringgasvelocityrelativeto thebucketWRR1. Theorientationofthebucketrootat entry of the gas should be approximately along line WRRI. The direction of the gas leaving the bucket is deter mined by the bucket exit angle and appears on the veloc itydiagramaslineWRR2. Theabsolutevelocityofgas leaving the bucket at the root radius is given by line 0R2. Once the vectors for the root radius have been estab lished as a reference, the proper blade angles at various radii can be constructed by the previously mentioned relation (1) As an example, the vectors for the bucket tip radius, de termined according to Equation 1, are shown in dotted 35 linesonFIG.3. Thefollowingpointsshouldbenoted. The vectors WRR1 and WTT1' which represent the veloc ities of the gas relative to the buckets at the bucket root andtiprespectivelyareorientedatdifferentangles. This manifests itself as a twist or warp in the bucket in order 3,135,496 Referring now to FIG. 1 of the drawing, the portion of the gas turbine shown includes an outer casing 1 support ing a group of circumferentially-spaced, radially-extend ingnozzlepartitions2. Theinnerendsofthenozzle partitionsareheldstationaryoninnerstatormember3.40 tocauseittoconformtothefreevortexconditionprevi~ A thintransitionwall4directshotgasesfromthecom bustion chamber 4a to an annular ?ow duct 5 preceding nozzles 2. The gas leaving nozzles 2 ?ows between buckets 6mountedontheperipheryoftheturbinewheel7. Other downstream nozzles and buckets (not shown) may extract additional energy from the gases. ouslyestablished. Similarly,thevectorsCR1and0T1’ representing the gas velocity leaving the nozzle, indicate that the nozzle is also warped to conform with the free vortexprinciple. The bucket tip pro?le 12 is cross-hatched to distinguish itfromtherootpro?le13. Theentryofthegasatthe root pro?le is along line 14, while the entry of the gas atthebuckettipisalongline16. Itshouldbenoted that root entry line 14 subtends a lesser angle with the tangentialline15thandoestherootentryline16. Simi larly, the direction of the gas leaving bucket 10 at the root is generally directed along the line 17, while that Reference to a typical “prior art” free vortex bucket as 45 showninFIGS.6and7willmakethisfactmoreapparent. FIG. 6 indicates a single bucket 10 disposed on base 11. Although the hot gas arriving at the flow annulus 5 would normally be made to have relatively uniform tem perature distribution, the temperature pro?le is altered in accordance with the invention by means of controlled jets of air directed substantially perpendicular to the hot gas ?ow by means of a series of pipes such as the one at 8. The gas injected through pipes 8 is substantially cooler than the hot gas leaving the combustion chamber and may be supplied from any suitable source, such as the compressorofthegasturbinepowerplant(notshown). 55 leavingthebucketatthetipisdirectedalongtheline A suitable regulating valve 9 may be manually or auto matically controlled to adjust the “temperature pro?le” radially across the passage 5. 18. Theselinesofgasentryandexitrelativetobucket 10 have their counterparts on the FIG. 3 velocity diagram of the typical free vortex bucket discussed, where the relative root entry line 14 corresponds to vector WRR1, FIG. 2 of the drawing indicates the “slanted” tempera ture pro?le obtained with the apparatus of FIG. 1. As 60 and the line of entry at the tip 16 corresponds to vector willbeseenfromFIG.2,thetemperatureA towardthe radially inner part of annulus 5 increases gradually to‘ a point B of much higher temperature toward the radially outerportionoftheannulus. ThetemperatureatA, therefore,correspondstotheroottemperatureofthe65 bladeistaperedfromroottotipincross-sectionalarea. blades, whereas the temperature B corresponds to the tip temperature and ismuch higher than for normal designs. It should be understood that the temperature of FIG. 2 is“stagnationtemperature”ortotaltemperatureT1,which includes both the kinetic and internal energy of the gas. According to one practice of turbine design, the nozzle and blade angles may be calculated at a particular radius of reference (here the root radius) by making certain routine assumptions, and then the gas velocities and blade In other words, the net cross-sectional area of the tip pro?le 12 is less than the net cross-sectional area of the rootprofile13. Thisisdoneinordertoreducetheroot stress and to provide a more suitable aerodynamic shape at the tip for the reduced turning angle of the relative gas stream. FIG. 4 of the drawing indicates the velocity diagram for a bucket constructed in accordance with the invention. The root or reference vectors are the same as in FIG. 3 inordertofacilitatecomparisonofthedesigns. The WTTI'. Line17ofFIG.6correspondstovectorWRRZ, While line 18 corresponds to WTT2’. FIGS. 6 and 7 indicate another common feature found inconventionalblading. ItwillbeobservedthatthePDF Image | FLOW TURBINE WITH RADIAL TEMPERATURE GRADIENT
PDF Search Title:
FLOW TURBINE WITH RADIAL TEMPERATURE GRADIENTOriginal File Name Searched:
US3135496.pdfDIY PDF Search: Google It | Yahoo | Bing
NFT (Non Fungible Token): Buy our tech, design, development or system NFT and become part of our tech NFT network... More Info
IT XR Project Redstone NFT Available for Sale: NFT for high tech turbine design with one part 3D printed counter-rotating energy turbine. Be part of the future with this NFT. Can be bought and sold but only one design NFT exists. Royalties go to the developer (Infinity) to keep enhancing design and applications... More Info
Infinity Turbine IT XR Project Redstone Design: NFT for sale... NFT for high tech turbine design with one part 3D printed counter-rotating energy turbine. Includes all rights to this turbine design, including license for Fluid Handling Block I and II for the turbine assembly and housing. The NFT includes the blueprints (cad/cam), revenue streams, and all future development of the IT XR Project Redstone... More Info
Infinity Turbine ROT Radial Outflow Turbine 24 Design and Worldwide Rights: NFT for sale... NFT for the ROT 24 energy turbine. Be part of the future with this NFT. This design can be bought and sold but only one design NFT exists. You may manufacture the unit, or get the revenues from its sale from Infinity Turbine. Royalties go to the developer (Infinity) to keep enhancing design and applications... More Info
Infinity Supercritical CO2 10 Liter Extractor Design and Worldwide Rights: The Infinity Supercritical 10L CO2 extractor is for botanical oil extraction, which is rich in terpenes and can produce shelf ready full spectrum oil. With over 5 years of development, this industry leader mature extractor machine has been sold since 2015 and is part of many profitable businesses. The process can also be used for electrowinning, e-waste recycling, and lithium battery recycling, gold mining electronic wastes, precious metals. CO2 can also be used in a reverse fuel cell with nafion to make a gas-to-liquids fuel, such as methanol, ethanol and butanol or ethylene. Supercritical CO2 has also been used for treating nafion to make it more effective catalyst. This NFT is for the purchase of worldwide rights which includes the design. More Info
NFT (Non Fungible Token): Buy our tech, design, development or system NFT and become part of our tech NFT network... More Info
Infinity Turbine Products: Special for this month, any plans are $10,000 for complete Cad/Cam blueprints. License is for one build. Try before you buy a production license. May pay by Bitcoin or other Crypto. Products Page... More Info
CONTACT TEL: 608-238-6001 Email: greg@infinityturbine.com (Standard Web Page)